Optimal Single Impulse De-orbit from Earth Orbits - OTB

Optimization Toolbox version of the deorbit.m MATLAB script which determines optimal de-orbit maneuvers.

This document describes a MATLAB script named deorbit_otb that can be used to compute the single optimal impulsive maneuver required to de-orbit a spacecraft in a circular or elliptical Earth orbit. The user provides the classical orbital elements of the initial orbit along with the desired geodetic altitude and relative flight path angle targets at the entry interface (EI).